<p>The paper presents the optimization of the new profile design for the compressor first stage rotor tip section, intended to operate over a wide range of regimes including off-design conditions, and its subsequent experimental validation. The optimization was achieved using CFD with the level of total pressure losses and width of the loss bucket as the selection criteria. The final optimized profile design was then subjected to experimental testing within a high-speed wind tunnel to validate its performance. During the experimental phase, special attention was given to addressing the challenge of non-unity axial velocity-density ratio (AVDR) values by employing “2.5D” numerical simulations, which enabled accurate comparisons between the experimental and simulated results. Furthermore, the empirical loss model was calibrated using the specific CFD data obtained for the newly designed profile, thereby refining its accuracy and applicability to this particular profile configuration. Overall, this study presents a comprehensive approach to optimize, experimentally validate, and refine the empirical loss model for a new profile design intended for the compressor first stage rotor tip section. The findings contribute to the advancement of profile design methodologies and enhance the understanding of their performance characteristics in various operating conditions.</p>